FR3097329A1 - Aircraft wheel and brake assembly - Google Patents

Abstract

An aircraft wheel and brake assembly, comprising a wheel (20), a brake (21) arranged to brake the wheel, and a measuring device (22) arranged to measure a speed of rotation of the wheel, the brake comprising at at least one friction member (29), an actuator support (26), and at least one brake actuator (27) carried by the actuator support and arranged to selectively exert a braking force on the friction member , the measuring device comprising a target (30) and a sensitive component (31) intended to produce a measuring signal representative of a rotational speed of the target, the aircraft wheel and brake assembly being arranged so that when the aircraft wheel and brake assembly is assembled, the target (30) is rotatably integral with the wheel and the sensitive component is mounted on the actuator carrier (26), the target and the sensitive component being arranged so that the sensitive component detects a rotation of the target.

Description

Aircraft wheel and brake assembly

The invention relates to the field of measuring the rotational speed of braked aircraft wheels.

BACKGROUND OF THE INVENTION

A braking system for the wheels of an aircraft comprises a plurality of brakes which each equip a so-called “braked” wheel of the aircraft. The braking system conventionally implements an anti-skid function of the braked wheels.

Measuring the rotational speed of the braked wheels when the aircraft is on the ground is a key element of the anti-skid function.

In addition to the brake, each braked wheel is equipped with a device for instantaneous measurement of its speed of rotation in order to detect the start of a lock: the "tachometer".

Traditionally, an aircraft wheel tachometer uses passive magnetic technology, such as variable reluctance for example. The tachometer generates an electrical measurement signal having as frequency the rotational frequency of the wheel or a multiple of the rotational frequency of the wheel.

The tachometer is installed at the axis of rotation of the wheel, usually in the axle or in the wheel cover. A sensitive component (or sensitive cell) of the tachometer detects either the angular position or a variation in the angular position of a target that is integral in rotation with the wheel.

Thus, with reference to figure 1, a first known solution consists in using a wheel cowl 1 fixed to rim 2 of wheel 3 and rotating with wheel 3 to drive a target 4 thanks to a drive device 5. The angular position or the speed of rotation of the wheel 3 is acquired by the sensitive component 6 which is fixed and which is positioned inside the axle 7 close to the target 4. The sensitive component 6 is connected by a cable 8 to the braking system and transmits the electrical measurement signal (analogue or digital) to it.

With reference to FIG. 2, a second known solution consists in using a wheel cowl 10 which this time is fixed to the axle 11, and therefore fixed, and to integrate the sensitive component 12 into the wheel cowl 10. The target 13 is secured to rim 14 of wheel 15 and is positioned between rim 14 and sensitive component 12. Sensitive component 12 is connected by a cable 16 to the braking system.

These solutions are relatively robust and efficient, but still have certain drawbacks.

The low speed sensitivity of variable reluctance tachometers is relatively poor, because the electrical measurement signals produced by these variable reluctance tachometers are too weak at low speed to be reliable.

Consideration has therefore been given to using active sensors, for example Hall effect sensors. Their sensitivity at low speed is better than that of variable reluctance tachometers.

However, the environment of the end of the axle undergoes significant temperature fluctuations related to the rise in temperature of the brake on landing, and the lowering of temperature during flight.

However, Hall effect sensors are more sensitive to the environment than passive magnetic sensors. In particular, their transfer function is modified by temperature and exhibits great variability during manufacture, so that the use of this technology requires measurements to be taken to compensate for these factors. The principle of Hall effect measurement may also require the presence of magnets with precise and stable characteristics over time. All this involves combining the measurement function with calibration and temperature compensation functions, which makes the use of this type of technology complex.

Consideration was also given to using solutions from other industrial fields. In industry, the measurement of the rotational speed of a rotating element is generally carried out by an encoder reporting the angular position on a digital bus (we speak of an "absolute encoder"), or else generating "tops" at regular intervals (we speak of “incremental encoder”). These encoders implement magnetic technology, generally Hall effect, or else optical technology.

The significant temperature fluctuations that have been mentioned create cycles of expansion and contraction of the materials which affect the effectiveness of the seals and which, over time, degrade the performance of the sensors requiring good sealing, such as the sensors optics.

Among the drawbacks of the known solutions, we also note that the current tachometers must be removed when removing a wheel and reinstalled when reassembling the wheel. However, since wheel disassembly and reassembly are quite frequent and high-precision tachometers are relatively fragile, the risk of damage due to handling during wheel disassembly and reassembly is very real and significant.

OBJECT OF THE INVENTION

The object of the invention is to improve the precision of the tachometer of an aircraft wheel and to increase its service life.

With a view to achieving this object, an aircraft wheel and brake assembly is proposed, comprising a wheel, a brake arranged to brake the wheel, and a measuring device arranged to measure a speed of rotation of the wheel, the brake comprising at least one friction member, an actuator support, and at least one braking actuator carried by the actuator support and arranged to selectively exert a braking force on the friction member, the measuring device comprising a target and a sensitive component intended to produce a measurement signal representative of a speed of rotation of the target, the aircraft wheel and brake assembly being arranged so that, when the aircraft wheel and brake assembly aircraft is assembled, the target is integral in rotation with the wheel and the sensitive component is mounted on the actuator support, the target and the sensitive component being arranged so that the sensitive component detects a rotation of the target.

Thus, in the aircraft wheel and brake assembly according to the invention, the sensitive component is mounted on the actuator support and is no longer located inside the axle or the cowl. It therefore undergoes less restrictive temperature cycles, which increases its lifespan. This configuration is compatible with the use of active sensors, which have better sensitivity than passive sensors, and in particular than variable reluctance sensors. As the sensitive component is located on the actuator support on the brake side, it is no longer necessary to handle it when removing and refitting the wheel. This again increases the life of the sensitive component, which is much less subject to the risk of damage associated with disassembling and reassembling the wheel.

There is also proposed an aircraft wheel and brake assembly such as that which has just been described, in which the target is mounted on a rim of the wheel and is positioned, according to an axis of rotation of the wheel, between the actuator support and wheel.

There is also proposed an aircraft wheel and brake assembly such as that which has just been described, in which the braking actuator is positioned, in a first radial direction perpendicular to an axis of rotation of the wheel, between the sensitive component and the axis of rotation of the wheel.

There is also proposed an aircraft wheel and brake assembly such as that which has just been described, in which the sensitive component is positioned, in a first radial direction perpendicular to an axis of rotation of the wheel, between the actuator brake and the axis of rotation of the wheel.

There is also proposed an aircraft wheel and brake assembly such as that which has just been described, in which the sensitive component and the target extend successively in an axial direction parallel to an axis of rotation of the wheel.

An aircraft wheel and brake assembly such as the one just described is also proposed, in which the sensitive component and the target extend successively in a second radial direction perpendicular to an axis of rotation of the wheel.

There is also proposed an aircraft wheel and brake assembly such as that which has just been described, in which the target is a toothed wheel with axial toothing.

There is also proposed an aircraft wheel and brake assembly such as that which has just been described, in which the target is a toothed wheel with radial teeth.

There is also provided an aircraft wheel and brake assembly such as that which has just been described, in which the target comprises a plurality of rows of teeth.

There is also proposed an aircraft wheel and brake assembly such as that which has just been described, in which the target comprises a reference tooth comprising an extra thickness so that the measurement signal has a particular shape when the sensitive component detects the reference tooth.

There is also proposed an aircraft wheel and brake assembly such as that which has just been described, comprising two sensitive components offset by half a period of a pattern of the target.

There is also proposed an aircraft wheel and brake assembly such as that which has just been described, comprising two sensitive components offset by an odd modulo of a quarter of a period of a pattern of the target.

There is also proposed an aircraft wheel and brake assembly such as that which has just been described, in which the sensitive component is a magnetic sensor.

An aircraft wheel and brake assembly such as the one just described is also proposed, in which the sensitive component is an optical sensor.

There is also proposed an aircraft wheel and brake assembly such as that which has just been described, in which the sensitive component is an ultrasonic sensor.

There is also proposed an aircraft landing gear comprising an aircraft wheel and brake assembly such as that which has just been described.

An aircraft comprising an aircraft landing gear such as that which has just been described is also proposed.

The invention will be better understood in the light of the following description of particular non-limiting embodiments of the invention.

Reference will be made to the attached drawings, among which:

FIG. 1 represents a view in section, according to a plane perpendicular to an axis of rotation of an aircraft wheel, of the wheel and of a first tachometer of the prior art;

FIG. 2 represents a view in section, according to a plane perpendicular to an axis of rotation of an aircraft wheel, of the wheel and of a second tachometer of the prior art;

FIG. 3 represents a view in section, along a plane perpendicular to an axis of rotation of a wheel, of an aircraft wheel and brake assembly according to a first embodiment of the invention;

FIG. 4 is a view similar to that of FIG. 3 but in more detail, a target of the measuring device being a target with radial teeth;

Figure 5 is a detail view of Figure 4;

FIG. 6 is a view similar to that of FIG. 3 but in more detail, a target of the measuring device being a target with axial teeth;

FIG. 7 represents the target and two sensitive components;

FIG. 8 is a graph comprising curves of electrical measurement signals obtained in a configuration in which the measurement device comprises two sensitive components offset by a quarter of a period of a pattern of the target;

Figure 9 is a graph similar to that of Figure 8, in a configuration where the target comprises two rows of teeth;

FIG. 10 represents a sensitive component and a target having a reference tooth having an extra thickness;

FIG. 11 is a graph comprising curves of electrical measurement signals obtained in the configuration of FIG. 10;

FIG. 12 represents a view in section, according to a plane perpendicular to an axis of rotation of a wheel, of an aircraft wheel and brake assembly according to a second embodiment of the invention;

FIG. 13 is a view similar to that of FIG. 12 but in more detail, a target of the measuring device being a target with radial teeth;

Figure 14 is a detail view of Figure 13;

FIG. 15 is a view similar to that of FIG. 12 but in more detail, a target of the measuring device being a target with axial teeth;

Figure 16 shows the target and two sensitive components.

Referring to Figure 3, an aircraft wheel and brake assembly according to a first embodiment of the invention comprises a wheel 20 of an aircraft landing gear, a brake 21 and a measuring device 22 of the angular velocity of the wheel 20.

The aircraft wheel and brake assembly according to a first embodiment of the invention is described while the latter is assembled.

The wheel 20 comprises a rim 23 which receives a tire 24 and which is rotatably mounted on an axle 25 located at the bottom of the undercarriage.

The brake 21 is intended to brake the wheel 20. The brake 21 is here a hydraulic brake. The brake 21 comprises an actuator support, in this case a crown 26, which carries at least one braking actuator, in this case a plurality of braking actuators 27. The crown 26 is mounted on the axle 25 .

A torsion tube 28 is fixed to the crown 26. The torsion tube 28 extends into the rim 23. The crown 26, and therefore the torsion tube 28, are stopped in rotation with respect to the axle 25 by stop means not shown here.

The brake 21 also comprises at least one friction member, in this case a stack of carbon discs 29 composed of rotors which are integral in rotation with the rim 23 and of stators which are integral in rotation with the torque tube 28.

The braking actuators 27 are arranged to selectively exert, when the pressurized fluid is admitted, a braking force on the carbon discs.

The measuring device 22 comprises a target 30 and a sensitive component 31 intended to produce an electrical measurement signal representative of the speed of rotation of the target 30.

The target 30 is here a metal toothed wheel which is mounted on the rim 23 of the wheel 20. By "mounted", it is meant that the target 30 is fixed directly on the rim 23, or else is fixed on a support itself. attached to rim 23.

Target 30 is positioned, along an axis of rotation X of wheel 20, between crown 26 and wheel 20.

The sensitive component 31, meanwhile, is mounted on the crown 26. Again, by "mounted", we mean that the sensitive component 31 is fixed directly on the crown 26, or is fixed on a support itself fixed on the crown 26.

The sensitive component 31 extends from one face of the crown 26 positioned facing an internal face of the wheel 20, said internal face of the wheel 20 being the face of the wheel 20 on the side of which the brake 21 is located. .

It can be seen that the braking actuator 27 which is close to the sensitive component 31 is positioned, in a first radial direction Y1 perpendicular to the axis of rotation X of the wheel 20, between the sensitive component 31 and the axis of rotation X of the wheel 20. In other words, the sensitive component 31 is located at an outer portion of the crown 26, close to the periphery or on the periphery of the crown 26.

It is noted that it would be perfectly possible to provide that the sensitive component 31 be positioned, in the first radial direction Y1 perpendicular to the axis of rotation X of the wheel 20, between the braking actuator 27 and the axis of rotation X of the wheel 20. In other words, the sensitive component 31 can also be located at an internal, central portion of the crown 26, close to the center thereof.

The measuring device 22 is here arranged in an axial configuration: the sensitive component 31 and the target 30 extend successively in an axial direction X1 parallel to the axis of rotation X of the wheel 20.

Referring to Figures 4 and 5, it can be seen that the target 30 can be a target with radial teeth: the teeth 32 extend from a main and central portion of the target in radial directions, that is to say perpendicular to the axis of rotation X of the wheel 20.

Referring to Figure 6, we see that the target 30 can be a target with axial teeth: the teeth 33 extend from a main and planar portion of the target in axial directions, that is to say parallel to the axis of rotation X of the wheel 20.

The sensitive component 31 is here a magnetic sensor, in this case a Hall effect sensor. The distance between the Hall effect sensor 31 and the target 30 is here between 1mm and 7mm.

The Hall effect sensor 31 is connected to a processing unit located in the fuselage of the aircraft or else on the landing gear or else in the axle 25. The connection here is a wired connection via the cable 35 but could be a wireless link. The processing unit can also be called calculator, controller, data concentrator, etc.

When a hollow is in front of the Hall effect sensor 31, the distance between the Hall effect sensor 31 and the nearest metallic mass is equal to d1 (see figure 5). When a tooth 32 (or 33) is opposite the Hall effect sensor 31, the distance between the Hall effect sensor 31 and the nearest metal mass is equal to d2.

The Hall effect sensor 31 thus produces an electrical measurement signal, in this case an analog signal, the amplitude of which depends on the presence of a tooth 32 or of a hollow in front of the Hall effect sensor 31. The Hall effect sensor 31 thus detects a rotation of the target 30.

The electrical measurement signal has a frequency which is proportional to the rotational speed of the target 30 and therefore to the rotational speed of the wheel 20. The processing unit acquires the electrical measurement signal and produces from the electrical signal measuring an estimate of the speed of rotation of the target 30 and therefore of the speed of rotation of the wheel 20.

Advantageously, with reference to FIG. 7, not one but several Hall effect sensors 31 are used.

The measuring device 22 is then robust to the presence of mechanical play and vibrations which affect the distance measurement and therefore the amplitude of the electrical measurement signal. In a frequency measurement system, as is the case here, amplitude variations can be tolerated, but it is preferable to reduce them in order to avoid measurement errors. The use of several Hall effect sensors 31 makes it possible to eliminate from the measurement the parasitic quantities which affect the Hall effect sensors 31 in the same way, such as the temperature, the deformations of the wheel or the vibrations undergone by the wheel. .

In this case, two Hall effect sensors 31 are used.

Here, the Hall effect sensors 31 are offset by half a period of the pattern of the target 30. A period of the pattern corresponds to a tooth 32 followed by a pit 36 (or vice versa).

The two electrical measurement signals produced by the two Hall effect sensors 31 represent the same response associated with the geometry of the target 30, with a half-period shift. The two electrical measurement signals are therefore in phase opposition.

The difference between the two electrical measurement signals is then produced (by calculation or by means of a digital or analog circuit). The amplitudes of the two electrical measurement signals, which are in phase opposition, will therefore be added. Conversely, local parasitic effects will be eliminated or at least attenuated during differentiation. Thus, for example, as the effects of vibrations in the axial directions affect the Hall effect sensors 31 in the same way, the effects of these vibrations compensate each other during the differentiation and are therefore eliminated or almost eliminated.

The measuring device 22 can also make it possible to determine the direction of rotation of the wheel 20. This information can be useful for functions other than braking. Among these functions, there is in particular a function for engaging the electric taxiing system while the aircraft is taxiing. There is also an odometry function to accurately estimate the position of the aircraft on the ground.

The Hall effect sensors 31 will thus be positioned in positions allowing both to implement the differentiation which has just been mentioned, and to determine the direction of rotation of the wheel 20.

Here, the two Hall effect sensors 31 are offset for this purpose by an odd modulo of a quarter of a period of the pattern of the target 30, for example 1/4, 3/4, or 5/4 of the pattern period. The choice depends in particular on the size of the teeth 32 and the diameter of the Hall effect sensor 31.

The curves visible in FIG. 8 correspond to a configuration in which the spacing between the two Hall effect sensors 31 is equal to a quarter of a period of the pattern.

Curve 40 represents the electrical measurement signal produced by a first Hall effect sensor. Curve 41 represents the electrical measurement signal produced by a second Hall effect sensor. Curve 42 represents a resulting signal equal to the difference between the two electrical measurement signals.

It can be seen that the resulting signal has a frequency that is a multiple of the rotational frequency of wheel 20. The resulting signal is cleared of local disturbances. The direction of rotation of wheel 20 is determined by the sign of the phase delay of the electrical measurement signal produced by the second Hall effect sensor (curve 41) with respect to the electrical measurement signal produced by the first Hall effect sensor ( curve 40): +π/2 for a rotation in a given direction, -π/2 for a rotation in the other direction.

It is also possible to improve the measurement in the following way.

It is known that the number of cycles per wheel revolution 20 is given by the number of teeth 32 of the target 30.

An increase in the number of cycles per revolution, for example, has the advantage of improving the measurement at lower speeds during braking. Indeed, the measurement time required to perform the measurement increases with the period of the pattern.

For example, if you want to measure a rotational speed of 1Hz, with a 100-tooth wheel, the measurement time of one period is 1/100Hz, i.e. 10ms. We can go down to 5ms by using the measure of a half-period of the pattern. It is not possible to measure the speed with a refresh rate better than 5ms, unless the number of cycles per revolution, and therefore the number of teeth, is increased. This number is limited by the diameter of the target (which is for example substantially equal to the diameter of the rim of the wheel), the number of teeth that it is possible to produce in such a diameter, and the angular resolution of the sensor at Hall effect.

We therefore use a target comprising several toothed wheels, i.e. several rows of teeth, each associated with their Hall effect sensor(s). In this way, a resulting signal is obtained at a frequency twice the number of teeth of each row (if two rows are used), and in this way the limitations linked to the technology which have just been mentioned are overcome.

The curves visible in FIG. 9 correspond to a configuration where two rows of teeth are used, the two rows of teeth being angularly offset by a quarter period of the pattern, which again makes it possible to determine the direction of rotation of the wheel 20.

Curve 45 represents the electrical measurement signal produced by the Hall effect sensor associated with a first row of teeth. Curve 46 represents the electrical measurement signal produced by the Hall effect sensor associated with a second row of teeth.

Curve 47 represents the resulting signal produced by combining the two electrical measurement signals. The number of cycles of the resulting signal is doubled compared to the number of cycles of the electrical measurement signals.

It may also be advantageous to determine the angular position of the wheel 20. This information is useful, for example, again, for the engagement function of the electric taxiing system when the aircraft is traveling at low speed. The speed of the taxiage motor, which drives the wheel 20 in rotation, must in fact be synchronized with the speed of rotation of the wheel 20 to allow meshing smoothly. The detailed knowledge of the position of the wheel 20, in addition to the knowledge of the speed of rotation of the wheel 20, makes it possible to insert the teeth of the meshing system into those of the wheel drive device without risk of clash between the two.

The determination of the angular position of the wheel 20 can also be used for the odometry function.

The angular position of the wheel 20 can be obtained thanks to the addition of a system making it possible to know the position of the teeth 32 of the target 30 with respect to an origin.

With reference to FIG. 10, an extra thickness 50 is added for this to a reference tooth 51 of the target 30. This extra thickness 50 modifies the distance between the Hall effect sensor 31 and the target 30 when the reference tooth 51 is located opposite the Hall effect sensor 31, said distance then being equal to d3 (and not to d2). The additional thickness 50 affects the amplitude of the electrical measurement signal obtained specifically for this position of the target 30: the electrical measurement signal comprises a particular form corresponding to detection by the measurement component of the reference tooth 51. sorts the origin of the angular position.

Thus, in FIG. 11, curve 53 represents an electrical measurement signal produced by the first Hall effect sensor, curve 54 represents an electrical measurement signal produced by the second Hall effect sensor 31, while curve 55 represents a resulting signal equal to the difference between the two electrical measurement signals. The zero crossing, that is to say the passage of the reference tooth 51 in front of the Hall effect sensor, can be detected by thresholding: the amplitude of the resulting signal is compared with a predetermined threshold S, and that the zero crossing occurs when the amplitude of the resulting signal is greater than said predetermined threshold S.

The angular position of the target 30 and therefore of the wheel 20 can then be obtained, for example by counting the cycles since the zero crossing. The angular position is therefore known to within 360°/N, where N is the number of teeth of the target 30.

Note that a measuring device with three sensors, in which the difference is made between the electrical measurement signal produced by a central sensor and the electrical measurement signals produced by the neighboring sensors, makes it possible to determine a precise angular position between two teeth.

It is also possible to choose, in a system with multiple rows of teeth, to differentiate the profile of each of the rows of teeth. This makes it possible to improve the measurement of the angular position, and in particular to allow absolute angular positioning of the wheel.

Referring to Figure 12, the measuring device 60 of an aircraft wheel and brake assembly according to a second embodiment of the invention can also be arranged in a radial configuration: the Hall effect sensor 61 and the target 62 extend successively in a second radial direction Y2 perpendicular to an axis of rotation X of wheel 63.

We see in Figure 12 that the target 62 is positioned between the Hall effect sensor 61 and the axle 64. Of course, the Hall effect sensor 61 could very well be positioned between the axle 64 and the target 62.

Referring to Figures 13 and 14, it can be seen that the target 62 can be a target with radial teeth: the teeth 66 extend from a main central portion of the target 62 in radial directions, that is to say perpendicular to the axis of rotation of the wheel.

When a hollow is in front of the Hall effect sensor 61, the distance between the Hall effect sensor and the nearest metal mass is equal to d1.

When a tooth 66 is opposite the Hall effect sensor 61, the distance between the Hall effect sensor 61 and the nearest metal mass is equal to d2.

With reference to FIG. 15, it can be seen that the target 67 can be a target with axial teeth: the teeth 68 extend from a flat main portion of the target 67 in axial directions, that is to say parallel to the axis of rotation X of the wheel 63.

Again, the electrical measurement signal produced by the Hall effect sensor 61 presents an electrical alternation resulting from the alternation between the teeth and the hollows of the target.

Advantageously, again, with reference to FIG. 16, not one but several are used, in this case two Hall effect sensors 61.

The difference is made between the two electrical measurement signals to improve the measurement and eliminate local parasitic effects.

Of course, the invention is not limited to the embodiments described but encompasses any variant falling within the scope of the invention as defined by the claims.

It has been described here that the sensitive component is a Hall effect sensor, and that the target is a toothed wheel. This configuration in no way limits the scope of the invention.

We note first of all that, whatever the technology used, the sensitive component can for example be a distance sensor or a detector.

The detector supplies an “all or nothing” type measurement signal depending on whether the distance between the detector and the target is greater than or not greater than a predefined threshold.

The distance sensor provides a measurement signal that depends on the distance between the sensor and the target, as is the case for a proximity sensor for example.

The measurement technology can be an inductive technology.

The sensitive component can then for example be an inductive proximity sensor. An inductive sensor will require a target made from a metallic material.

The measurement technology may be magnetic technology. The sensor is for example, as described in this application, a Hall effect sensor. It could also be advantageous to replace the toothed wheel with a wheel equipped with magnets.

The range of the inductive and magnetic technologies can be greater than 10mm, which makes it possible to have a measurement device compatible with the effects of deformations and vibrations of the wheel during the braking of the aircraft and/or the turns made by the 'aircraft.

Ultrasonic technology can also be used. Ultrasonic sensors and detectors are particularly effective for measuring distances of several centimeters. They also allow measurement on non-metallic materials, which makes it possible to use targets made of lighter composite materials.

Optical technology is also possible. Optical sensors and detectors are also suitable for centimeter measurement distances, and have the advantage of allowing measurement on any target material of sufficient opacity.

Thus, in the first embodiment, that is to say when the measuring device is arranged in an axial configuration (see FIGS. 3 to 6), the measuring distance can reach several centimeters, in particular to take account of the deformations or vibration of the wheel. Ultrasonic measurement could then be the most suitable.

The brake of the wheel and brake assembly is of course not necessarily a hydraulic brake but can be an electromechanical brake. The actuator support in this case is an actuator support.

The target is not necessarily mounted on the rim of the wheel, but could for example be formed on or in the tire.

Claims (17)

Aircraft wheel and brake assembly, comprising a wheel (20; 63), a brake (21) arranged to brake the wheel, and a measuring device (22; 60) arranged to measure a rotational speed of the wheel, the brake comprising at least one friction member (29), an actuator support (26), and at least one braking actuator (27) carried by the actuator support and arranged to selectively exert a braking force on the friction member, the measuring device comprising a target (30; 62) and a sensitive component (31; 61) intended to produce a measurement signal representative of a speed of rotation of the target, the wheel assembly and aircraft brake being arranged so that, when the aircraft wheel and brake assembly is assembled, the target (30; 62) is integral in rotation with the wheel and the sensitive component is mounted on the actuator support (26), the target and the sensitive component being arranged such that the sensitive component detects a rotation of the ci wheat. Aircraft wheel and brake assembly according to Claim 1, in which the target (30; 62) is mounted on a rim (23) of the wheel and is positioned, along an axis of rotation of the wheel (X), between the actuator support and the wheel. Aircraft wheel and brake assembly according to one of the preceding claims, in which the braking actuator (27) is positioned, in a first radial direction (Y1) perpendicular to an axis of rotation of the wheel, between the component sensitive (31; 61) and the axis of rotation of the wheel. Aircraft wheel and brake assembly according to one of Claims 1 or 2, in which the sensitive component (31; 61) is positioned, in a first radial direction (Y1) perpendicular to an axis of rotation of the wheel, between the brake actuator (27) and the rotation axis of the wheel. Aircraft wheel and brake assembly according to one of the preceding claims, in which the sensitive component and the target extend successively in an axial direction (X1) parallel to an axis of rotation of the wheel. Aircraft wheel and brake assembly according to one of Claims 1 to 4, in which the sensitive component and the target extend successively in a second radial direction (Y2) perpendicular to an axis of rotation of the wheel. An aircraft wheel and brake assembly according to any preceding claim, wherein the target is an axially toothed gear. An aircraft wheel and brake assembly according to one of claims 1 to 6, wherein the target is a radially toothed gear wheel. An aircraft wheel and brake assembly according to claim 7 or 8, wherein the target comprises a plurality of rows of teeth. Aircraft wheel and brake assembly according to one of Claims 7 to 9, in which the target comprises a reference tooth (51) comprising an extra thickness (53) so that the measurement signal has a particular shape when the component sensitive detects the reference tooth. Aircraft wheel and brake assembly according to one of the preceding claims, comprising two sensitive components (31; 61) offset by half a period of a pattern of the target. Aircraft wheel and brake assembly according to one of Claims 1 to 10, comprising two sensitive components (31; 61) offset by an odd modulo of a quarter of a period of a pattern of the target. Aircraft wheel and brake assembly according to one of the preceding claims, in which the sensitive component (31; 61) is a magnetic sensor. Aircraft wheel and brake assembly according to one of the preceding claims, in which the sensitive component (31; 61) is an optical sensor. Aircraft wheel and brake assembly according to one of the preceding claims, in which the sensitive component (31; 61) is an ultrasonic sensor. Aircraft lander comprising an aircraft wheel and brake assembly according to one of the preceding claims. Aircraft comprising an aircraft landing gear according to claim 16.